On-Wing Reprogramming of the Electronic Engine Control (EEC) [CFML]

TASK 73-21-55-860-802-A
On-Wing Reprogramming of the Electronic Engine Control (EEC)

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.

1. Reason for the Job
To upgrade the EEC software version.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	AR	WARNING NOTICE(S)
9471M34	1	PMAT CABLE ASSEMBLY
ALT45200001	1	PORTABLE DATA LOADER

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
437AL, 438AR
FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
447AL, 448AR

C. Referenced Information

REFERENCE	DESIGNATION
TASK 22-97-00-710-001-A	Operational Test of the LAND CAT III Capability
TASK 24-41-00-861-002-A	Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-861-002-A-01	Energize the Aircraft Electrical Circuits from the APU
TASK 24-41-00-861-002-A-02	Energize the Aircraft Electrical Circuits from Engine 1(2)
TASK 24-41-00-862-002-A	De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01	De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02	De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 71-00-00-750-804-A	One Shot Trim Balance
TASK 71-13-00-010-803-A	Opening of the Fan Cowl Doors
TASK 71-13-00-410-803-A	Closing of the Fan Cowl Doors
TASK 73-21-50-860-801-A	Programming of the Data Entry Plug (DEP)
TASK 73-29-00-710-802-A	FADEC Test (Menu Mode)
TASK 73-29-00-710-804-A	Weight Configuration (Menu Mode)
TASK 73-29-00-710-808-A	Nacelle Anti-Icing (NAI) Valve Lock Open (Menu Mode)
TASK 73-29-00-740-809-A	Read the LRU Identification Report (Menu Mode)
TASK 73-29-00-740-810-A	Entry of the Engine Serial Number (ESN) (Menu Mode)
TASK 73-29-00-740-824-A	Accelerometer Configuration via the Menu Mode
TASK 79-36-00-740-801-A	Oil Debris Reset (Menu Mode)
EEC Reprogramming Cable (9471M34)
EEC Programming Cable Continuity Test
PMAT 2000 to Ethernet Cable Connection
EEC Software Part Number

3. Job Set-up
Subtask 73-21-55-861-054-A

A. Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).

Subtask 73-21-55-740-054-A

B. Print a report of the Line Replaceable Unit (LRU) IDENTIFICATION page of the Multipurpose Control and Display Unit (MCDU) (Ref. AMM TASK 73-29-00-740-809) and of the fan balance weight configuration page of the MCDU (Ref. AMM TASK 73-29-00-710-804) and of the Nacelle Anti-Icing (NAI) lock open configuration page of the MCDU (Ref. AMM TASK 73-29-00-710-808).

(1) If EEC channel B is reprogrammed, print a report of the Oil Debris Monitoring System (ODMS) chip count (Ref. AMM TASK 79-36-00-740-801).
(2) Keep the reports.
(3) Do a Full Authority Digital Engine Control (FADEC) menu mode test on the EEC(s) that will be reprogrammed (Ref. AMM TASK 73-29-00-710-802) and print out the results of the test(s).
(4) If SW2 does not display on LRU report, replace EEC before you continue with reprogramming of OMAP software.

Subtask 73-21-55-840-050-A

C. Before you reprogram the EEC with new software, refer to the applicable Airbus Service Bulletin. It is important that the new EEC/software version agrees with the Airbus interchangeability requirements. Check with the airline configuration management document.

NOTE: If both EECs were reprogrammed at the same time, make sure that the EEC software have compatible configurations on the two engines (refer to the Power Plant Illustrated Parts Catalog (PIPC)).

NOTE: If the EEC software configurations on the two engines are not compatible, refer to the PIPC and program again the two ECC channels, as necessary.

Subtask 73-21-55-760-050-A

D. Reprogramming Kit - Battery Charge and Cable Continuity Self-Test.
(1) Disconnect the 'Dust Cap' on the 'GSE Vibration DSP Ethernet' on the left hand side of the reprogramming cable.
(2) Connect the one end of the Ethernet cable from the 'GSE Vibration DSP Ethernet' on the left hand side of the Reprogramming Box.
(3) Disconnect the 'Dust Cap' on the 'GSE Ethernet' on the right hand side of the Reprogramming Box.
(4) Connect the other end of the Ethernet Cable to the 'GSE Ethernet' on the right hand side of the Reprogramming Box.
(5) The 'BATTERY FULLY CHARGED' light illumination shows the battery is charged.

NOTE: If the 'BATTERY FULLY CHARGED' light does not illuminate, replace the standard 9V battery on the Reprogramming Box.

(6) Disconnect the 'Dust Cap' on the 'Tester Receptacle' on the Reprogramming Box.
(7) Connect the end of the reprogramming box cable (used for connecting to the EEC J9 connector) to the 'Tester Receptacle' on the Reprogramming Box.
(8) The 'Cable OK' light illumination shows the cable is in serviceable condition.

NOTE: If the 'Cable OK' light does not illuminate, re-test by replacing the batteries on the kit before replacing the Reprogramming Box.

(9) Put the 'Dust Cap' on the 'Tester Receptacle'.
(10) Disconnect both ends of the Ethernet Cables.
(11) Connect the 'Dust Caps' on 'GSE Vibration DSP Ethernet' on the left hand side and 'GSE Ethernet' on the right hand side of the reprogramming box.

Subtask 73-21-55-941-056-A

E. Safety Precautions
(1) On the center pedestal, on ENG panel 115VU:
(a) Make sure that the ENG/MODE selector switch is in the NORM position.
(b) Make sure that the ENG/MASTER 1(2) control switch was in the OFF position not less than five minutes before you do this procedure.
(c) Put WARNING NOTICE(S) in position to tell persons not to operate:

The ENG/MODE selector switch, and
The ENG/MASTER 1(2) control switch.

(2) On the ENG section of maintenance panel 50VU:
(a) Make sure that the ON legend of the FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) in position to tell persons not to energize FADEC 1(2).

Subtask 73-21-55-010-056-A

F. Get Access
(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-803):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
437AL 438AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
447AL 448AR

4. Procedure
Subtask 73-21-55-740-055-A

A. Reprogramming set-up with the ALT45200001 PORTABLE DATA LOADER (refer to the manufacturer's notice).
(1) Follow instructions given by the manufacturer's notice to copy on the PMAT2000 DATA KIT SECURE the media disk with P/N per applicable Airbus Service Bulletin. Check with the airline configuration management document.
(2) Refer to CFM SB 72-0042 to configure the network on the PMAT2000.

Subtask 73-21-55-740-056-A

B. On-wing software loading with the ALT45200001 PORTABLE DATA LOADER.

NOTE: The following procedure is based on the PMAT2000 DATA KIT SECURE P/N P2KABF02. For on-wing reprogramming of the EEC with other PDL P/N, follow the instructions given in the PDL manufacturer's notice for Para. 4.B.(1) to 4.B.(22).

NOTE: The software is installed one channel at a time. You must do the same steps again for the second channel.

(1) Make sure that the EEC power is OFF (the ON legend of the FADEC GND PWR ENG X pushbutton switch is off - engine OFF condition - no core rotation).
(2) Connect the test connector end of the 9471M34 PMAT CABLE ASSEMBLY (3) to the test connector of the EEC (J9).

EEC Reprogramming Cable (9471M34)

(3) Connect the Ethernet cable to the 9471M34 PMAT CABLE ASSEMBLY at either:

(a) The GSE Ethernet port to reprogram the control software or PHM software or
(b) The GSE vibration DSP Ethernet port to reprogram the field loadable OMAP software.

NOTE: Use a "straight" Ethernet cable. Do not use a "cross-over" Ethernet cable which is provided with a PMAT. If you use a cross-over Ethernet cable, the PMAT will not be able to find an EEC target to connect with for software upload.

(4) Connect the RJ45 ADAPTER CABLE 80079-1 (part of ALT45200001 PORTABLE DATA LOADER) to the reprogramming port of the ALT45200001 PORTABLE DATA LOADER.

PMAT 2000 to Ethernet Cable Connection

(5) Connect the other end of the Ethernet cable to the RJ45 ADAPTER CABLE 80079-1 (part of ALT45200001 PORTABLE DATA LOADER).

PMAT 2000 to Ethernet Cable Connection

(6) Follow the instructions given in the manufacturer's notice to load the EEC with the software P/N per the applicable Airbus Service Bulletin.
(7) If not already active, select the "PMAT Main Menu" icon on the PMAT desktop to open the loading software.
(8) Select the ARINC 615A DATALOADER on the PMAT Main Menu.
(9) Power the EEC by pushing the ENG/FADEC GND PWR switch on the 50VU. The ON legend will come on.
(10) Select one of these connection types on the PMAT:

To reprogram the control software or the PHM software, select "[...] EEC CH.X CPU", where "X" is the EEC channel and "[...]" is related to the PMAT network configuration file
To reprogram the field loadable OMAP software, select "[...] EEC CH.X DSP", where "X" is the EEC channel and "[...]" is related to the PMAT network configuration file
If the connection types given above are not available, select "615A LOADER STANDARD".

(11) Select "Continue".
(12) Select "Upload".
(13) Wait for the screen to show the EEC as an available target. The target hardware will be listed as "GEC-EECCPU_X", where X is the channel. Select this as a target.

NOTE: If you reprogram the control or PHM software, the target hardware will be listed as GECEECCPU_X, where X is the EEC channel.

NOTE: If you reprogram the field loadable OMAP software, there will be a delay of up to 3 minutes between EEC power-on and when the target appears.

NOTE: If you reprogram the OMAP software, the screen will display the target name as GECEECDSP CH-A and display the target hardware as GEC-EECDSP_A.

(14) Select "Continue".
(15) Select "ANY TAIL" and scroll through the list of parts to select the Engineering Release Number of the CPU software mentioned in the CFM SB (L1AXXXX).
(16) Select "Continue".
(17) Select "Continue Upload".
(18) Once the status bar indicates a complete load (and turns green), power down the EEC.
(19) If you reprogram the control, PHM and OMAP software, do Para. 4.B.(4) thru 4.B.(18) again with the appropriate port and associated software.
(20) Disconnect the test connector end of the 9471M34 PMAT CABLE ASSEMBLY from the test connector.
(21) Repeat Para. 4.B.(1) thru 4.B.(4) to connect the other channel for software loading.

NOTE: If the GO BACK button was selected after the first channel was loaded, go back and do Para. 4.B.(5) thru 4.B.(10) again.

(22) Do Para. 4.B.(7) thru 4.B.(18) again to continue the loading of the software on the second channel.

Subtask 73-21-55-710-055-A

C. Test
(1) Verify that the cross channel EEC contains the same EEC software part number that was just installed, read the LRU identification report (Ref. AMM TASK 73-29-00-740-809).
(a) If the EEC software part numbers are different, a new EEC software upload is required before proceeding to the next step.

NOTE: The EEC software part number is also available on the EEC software identification tag and should be the same as the one given by the LRU ident report.

EEC Software Part Number

(2) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).

CAUTION: MAKE SURE THAT YOU POWER CYCLE THE EEC TWICE TO PREVENT AN EGT INCREASE DURING THE NEXT TAKEOFF.

(a) Push the FADEC GND PWR pushbutton switch ON.
(3) Do the tests that follow:

CAUTION: IF YOU REPROGRAM THE TWO EEC CHANNELS, YOU MUST ENTER THE INSTALLED FAN-BALANCE WEIGHTS IN THE EEC MEMORY THROUGH THE WEIGHT CONFIGURATION MENU MODE. IF YOU DO NOT OBEY THIS INSTRUCTION, THE CALCULATION OF THE FAN TRIM BALANCE CAN GIVE INCORRECT RESULTS, WHICH CAN CAUSE FAN UNBALANCE.

(a) If only one EEC is reprogrammed, the EEC memory will be erased for this channel but the weight configuration values will be copied from the cross channel, after the engine serial number has been entered through the menu mode on the reprogrammed EEC.
(b) Do the engine serial number entry on the reprogrammed EEC (Ref. AMM TASK 73-29-00-740-810) or EECs (if both were reprogrammed).

NOTE: The engine serial number is available on the engine data plate.

NOTE: If you reprogram the two EEC channels, the EEC weight configuration is erased.

(c) If both EECs were reprogrammed at the same time, input the engine trim balance weight configuration to EEC memory on either one of the EEC channels. The weight configuration will automatically be saved to the other EEC channel (Ref. AMM TASK 73-29-00-710-804).

NOTE: If the weight configuration was not printed before the software was programmed, you can get the weights manually if you do an inspection of the installed weights on the platform front shroud (Ref. AMM TASK 71-00-00-750-804).

(d) If the NAI Lock Open configuration print-out indicated that either of the NAI valves (PRSOV1 or PRSOV2) were locked open, then this will need to be re-entered on the reprogrammed EEC(s). The default condition after EEC reprogramming is that the valves are not locked open. To lock open PRSOV1, perform the NAI Lock Open menu mode function on EEC channel A. To lock open PRSOV2, perform the NAI Lock Open menu mode function on EEC channel B (Ref. AMM TASK 73-29-00-710-808).
(e) If EEC channel B was reprogrammed and the LRU Identification Report print-out indicated that the ACCEL CONFIG "TCF" or "PX36" was active, then this will need to be entered again on the reprogrammed EEC channel B. Do the accelerometer configuration menu mode on EEC channel B (Ref. AMM TASK 73-29-00-740-824).
(f) Read the LRU Identification Report on both EEC channels and verify that the following items are consistent on both EECs and with actual engine configuration (refer to the applicable Airbus Service Bulletin for software part numbers) and airline configuration management document (Ref. AMM TASK 73-29-00-740-809).
1 Engine Thrust Rating and Type

NOTE: Engine thrust rating is available on the engine data plate.

2 EEC Control Software Part Number (SW1)

NOTE: The EEC Control software part number is available on the EEC software identification tag.

NOTE: Verify that the EEC software engine intermix/interchangeability is allowed per the applicable Airbus Service Bulletin.

3 EEC OMAP Software Part Number (SW2)

NOTE: Make sure that the OMAP Software PN (SW2) is the same on both EEC channels. In some cases, the OMAP SW part numbers between channels can differ by a trailing "0". If the only difference is the trailing "0", it is permitted.

4 N1 TRIM

NOTE: N1 trim level (0 through 7) is available on the engine data plate.

5 BUMP

NOTE: Option will read "Y" or "N" depending on bump availability.

6 ENGINE S/N

NOTE: The engine serial number is available on the engine data plate.

7 HW CONFIG

NOTE: The Hardware Configuration value is available in Table 2, for applicable engine thrust ratings and types (Ref. AMM TASK 73-21-50-860-801).

8 HPT DETERIORATION

NOTE: Must read N.

9 EEC PHM Software Part Number (SW3)
10 MTC CONFIGURATION

NOTE: Option will read "SINGLE" or "DUAL".

11 Accelerometer Configuration

NOTE: Option will read "NORM", "TCF" or "PX36".

12 Aircraft Type.
(g) If EEC channel B was reprogrammed, do the Oil Debris Reset Menu Mode and enter the cumulative chip count that was printed before the reprogramming (Ref. AMM TASK 79-36-00-740-801).
(h) Do a FADEC menu mode test on the reprogramming EEC (Ref. AMM TASK 73-29-00-710-802) or EECs (if both were reprogrammed).
1 Compare the FADEC menu mode test results to the print out of the FADEC menu mode test results performed prior to reprogramming. If no new faults were recorded, then the reprogramming was successful.
(i) Test for operate the aircraft in actual CAT III conditions (Ref. AMM TASK 22-97-00-710-001).
(j) Push the FADEC GND PWR pushbutton switch OFF.
1 De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
(k)

EEC Software Part Number

Subtask 73-21-55-869-057-A

D. Put the aircraft back to its initial configuration.
(1) On the overhead maintenance panel 50VU:
(a) Push the FADEC GND PWR 1(2) pushbutton switch (the ON legend goes off).

5. Close-up
Subtask 73-21-55-862-056-A

A. De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).

Subtask 73-21-55-410-053-A

B. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-803):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
437AL 438AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
447AL 448AR
(3) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 03:05:08 UTC